Double-power driven single-wing fixed-wing aircraft

A dual-power drive, fixed-wing technology, applied in the field of fixed-wing aircraft, can solve the problems of low aircraft safety performance, short aircraft endurance, no engine group, etc., and achieve the effect of shortening take-off distance, increasing endurance time, and improving power.

Inactive Publication Date: 2008-05-21
贵州贵航无人机有限责任公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, due to the high fuel consumption of the turbo-thrust engine, the flight time of the aircraft is relatively short.
In addition, most of the existing aircraft are only

Method used

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  • Double-power driven single-wing fixed-wing aircraft
  • Double-power driven single-wing fixed-wing aircraft
  • Double-power driven single-wing fixed-wing aircraft

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0022] Embodiment 1 of the present invention: the present invention is as figure 1 Shown, it comprises the fuselage 1 of existing aircraft, the wing 2 that is connected on the fuselage 1 and the landing gear 3 that is connected under the fuselage 1, turbo thrust engine 4 and propeller engine are installed on the aircraft, its common or Constitute power system of the present invention respectively, and adopt the mode of pulling forward and pushing back to provide power for fixed-wing aircraft; Existing electric pitch variable mechanism 9 is installed on propeller engine, and it can make the blade of propeller engine move in the direction of turbine thrust engine 4. Be in the feathering position when working independently, that is, the blade chord (the connection between the leading edge and the trailing edge of the blade is called the blade chord) is parallel to the fuselage, so as to reduce the resistance of the present invention when flying The propeller engine can use a pull...

Embodiment 2

[0024] Embodiment 2 of the present invention: the present invention is as figure 2 Shown, it comprises the fuselage 1 of existing aircraft, the wing 2 that is connected on the fuselage 1 and the landing gear 3 that is connected under the fuselage 1, turbo thrust engine 4 and propeller engine are installed on the aircraft, its common or Constitute power system of the present invention respectively, and adopt the mode of pulling forward and pushing back to provide power for fixed-wing aircraft; Existing electric pitch variable mechanism 9 is installed on propeller engine, and it can make the blade of propeller engine move in the direction of turbine thrust engine 4. Be in the feathering position when working independently, that is, the blade chord (the connection between the leading edge and the trailing edge of the blade is called the blade chord) is parallel to the fuselage, so as to reduce the resistance of the present invention when flying The propeller engine can use the p...

Embodiment 3

[0026] Embodiment 3 of the present invention: the present invention is as image 3 Shown, it comprises the fuselage 1 of existing aircraft, the wing 2 that is connected on the fuselage 1 and the landing gear 3 that is connected under the fuselage 1, turbo thrust engine 4 and propeller engine are installed on the aircraft, its common or Constitute power system of the present invention respectively, and adopt the mode of pulling forward and pushing back to provide power for fixed-wing aircraft; Existing electric pitch variable mechanism 9 is installed on propeller engine, and it can make the blade of propeller engine move in the direction of turbine thrust engine 4. Be in the feathering position when working independently, that is, the blade chord (the connection between the leading edge and the trailing edge of the blade is called the blade chord) is parallel to the fuselage, so as to reduce the resistance of the present invention when flying The propeller engine can use the th...

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PUM

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Abstract

The invention discloses a fixed wing aircraft of a single aircraft wing driven by dual powers, comprising the body of the aircraft, an aircraft wing connected with the body and a undercarriage connected with the body or below the aircraft wing; the aircraft is provided with a turbine push engine and a prop engine which together or respectively constitute the power system of the fixed wing aircraft and provide power for a fixed wing aircraft by forward-pulling and backward-pushing type. The invention can generate powerful flying power, can greatly improve the flying speed when the aircraft takes off or accelerates and can effectively shorten the taking off distance. The invention can reduce the oil consumption, thus increasing the duration of flight. When the invention singly uses a turbine push engine, an electric changeable pitch mechanism can lead the blade of the engine to be in smooth-oar position, thus reducing the flying resistance. Furthermore, the invention is provided with two engines; once one engine breaks down, the other engine can replace the engine, thus greatly improving the flying safety.

Description

technical field [0001] The invention relates to a fixed-wing aircraft, in particular to a single-wing fixed-wing aircraft driven by dual power. Background technique [0002] At present, the power system of an existing aircraft is usually constituted by one of a propeller engine or a turbine thrust engine. When the aircraft is required to have a long flight time, propeller engines are generally used, such as piston engines, turboshaft propeller engines, and rotor propeller engines. However, the backward thrust or forward pulling force of the propeller engine is weak, and the reverse thrust or pulling force received by the aircraft is also weak, so that the flying speed is low; when the flying speed of the aircraft is required to be high, the direct thrust gas is generally used. Turbine engines, such as turbojet or turbofan engines. However, due to the high fuel consumption of the turbo-thrust engine, the flight time of the aircraft is relatively short. In addition, most ex...

Claims

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Application Information

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IPC IPC(8): B64D27/00
Inventor 杨绍文
Owner 贵州贵航无人机有限责任公司
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